The Experts below are selected from a list of 1530 Experts worldwide ranked by ideXlab platform
吉田 優介 - One of the best experts on this subject based on the ideXlab platform.
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EVALUATION METHODS FOR FLIGHT HANDLING QUALITIES OF SMALL AIRCRAFT
法政大学大学院理工学・工学研究科, 2016Co-Authors: 吉田 優介Abstract:A new category of small aircrafts called LSA (Light Sports Aircraft) has been popular in the world. LSA is regarded as new basic aircraft not only for beginner’s flight training but also engineering educational fields. For beginners, easy handling of flight should be important and it is required to establish the quantitative evaluation methodologies of flight handling qualities for the aircraft design. In this study, measurement system of flight control and motion of the aircraft were installed in a motor-glider which specifications are almost same as LSA and relationships between flight control and aircraft motion on basic maneuver. In addition, relationships between Aerodynamic Derivative coefficients and flight handling qualities were clarified by sensory test with flight simulator
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Evaluation methods for handling qualities of small aircraft
2016Co-Authors: 吉田 優介Abstract:A new category of small aircrafts called LSA (Light Sports Aircraft) has been popular in the world. LSA is regarded as new basic aircraft not only for beginner’s flight training but also engineering educational fields. For beginners, easy handling of flight should be important and it is required to establish the quantitative evaluation methodologies of flight handling qualities for the aircraft design. In this study, measurement system of flight control and motion of the aircraft were installed in a motor-glider which specifications are almost same as LSA and relationships between flight control and aircraft motion on basic maneuver. In addition, relationships between Aerodynamic Derivative coefficients and flight handling qualities were clarified by sensory test with flight simulator.修士(工学)法政大学 (Hosei University
Rui Xiaotin - One of the best experts on this subject based on the ideXlab platform.
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Aerodynamic Derivative and Aerodynamic heating simulation and computation of spinning vehicle
Computer Simulation, 2014Co-Authors: Chen Dongyan, Rui XiaotinAbstract:Based on the shear stress transport( SST) k-ω turbulent model,M910 bullet and F4 spinning missiles' Aerodynamic characteristics were simulated numerically in different attack of angle and different Mach number. Drag,normal force,pitching damping,rolling damping moment and Magnus moment coefficients were calculated by the method which combines CFD code and empirical formula. The results were compared with the experimental data and the error is mainly within the error of engineering. These results verifies the accuracy of the simulation method. Meanwhile,the results of these missiles' temperature contours and the temperature distribution of the center line of missiles' windward side in the condition of different spinning speed and different angle of attack were calculated. The results provide valuable reference for spinning missile's aero-thermo-elastic simulation.
Andrews, Stuart P. - One of the best experts on this subject based on the ideXlab platform.
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Modelling and simulation of flexible aircraft : handling qualities with active load control
Cranfield University, 2011Co-Authors: Andrews, Stuart P.Abstract:The study of the motion of manoeuvring aircraft has traditionally considered the aircraft to be rigid. This simplifying assumption has been shown to give quite accurate results for the flight dynamics of many aircraft types. As modern transport aircraft have developed however, there has been a marked increase in the size and weight of these aircraft. This trend is likely to continue with the development of future blended-wing-body and supersonic transport aircraft. This increase in size and weight has brought about a unique set of aeroelastic and handling quality issues. The Aerodynamic forces and moments acting on an aeroplane have traditionally been represented using the Aerodynamic Derivative approach. It has been shown that this quasisteady Aerodynamic model inadequately predicts the aircraft’s stability characteristics, and that the inclusion of unsteady Aerodynamics “greatly improves the fidelity” of aircraft models. This thesis thus presents a novel numerical simulation of an aeroelastic aeroplane for real-time analysis. The model is built around the standard six degree-of-freedom equations of motion for a rigid aeroplane using the mean-axes system, and includes unsteady Aerodynamics and structural dynamics. This is suitable for pilot-in-the-loop simulation, handling qualities and flight loads analysis, and control law development. The dynamics of the structure are modelled as a set of normal modes, and the equations of motion are realised in state-space form. The unsteady Aerodynamic forces acting on the aeroplane are described by an indicial state-space model, including unsteady tailplane downwash and compressibility effects. An implementation of the model is presented in the MATLAB/ Simulink environment. The interaction between the flight control system, the aeroelastic system and the rigidbody motion of the aeroplane can result in degraded handling qualities, excessive actuator control, and fatigue problems. The introduction of load alleviation systems for the management of loads due to manoeuvres and gusts is also likely to result in the handling qualities of the aeroplane being degraded. This thesis presents a number of studies into the impact of structural dynamics, unsteady Aerodynamics, and load alleviation on the handling qualities of a flexible civil transport aeroplane. The handling qualities of the aeroplane are assessed against a number of different handling qualities criteria and flying specifications, including the Neal-Smith, Bandwidth, and CAP criterion. It is shown that aeroelastic effects alter the longitudinal and lateral-directional characteristics of the aeroplane, resulting in degraded handling qualities. Manoeuvre and gust load alleviation are similarly found to degrade handling qualities, while active mode control is shown to offer the possibility of improved handling qualities
Chen Dongyan - One of the best experts on this subject based on the ideXlab platform.
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Aerodynamic Derivative and Aerodynamic heating simulation and computation of spinning vehicle
Computer Simulation, 2014Co-Authors: Chen Dongyan, Rui XiaotinAbstract:Based on the shear stress transport( SST) k-ω turbulent model,M910 bullet and F4 spinning missiles' Aerodynamic characteristics were simulated numerically in different attack of angle and different Mach number. Drag,normal force,pitching damping,rolling damping moment and Magnus moment coefficients were calculated by the method which combines CFD code and empirical formula. The results were compared with the experimental data and the error is mainly within the error of engineering. These results verifies the accuracy of the simulation method. Meanwhile,the results of these missiles' temperature contours and the temperature distribution of the center line of missiles' windward side in the condition of different spinning speed and different angle of attack were calculated. The results provide valuable reference for spinning missile's aero-thermo-elastic simulation.
Yu Jingyi - One of the best experts on this subject based on the ideXlab platform.
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an improved nonlinear Aerodynamic Derivative model of aircraft at high angles of attack
International Journal of Aerospace Engineering, 2021Co-Authors: Mi Baigang, Yu JingyiAbstract:The classical Aerodynamic Derivative model is widely used in flight dynamics, but its application is extremely limited in cases with complicated nonlinear flows, especially at high angles of attack. A modified nonlinear Aerodynamic Derivative model for predicting unsteady Aerodynamic forces and moments at a high angle of attack is developed in this study. We first extend the higher-order terms to describe the nonlinear characteristics and then introduce three more influence parameters, the initial angle of attack, the reduced frequency, and the oscillation amplitude, to correct the constant Aerodynamic Derivative terms that have higher-order polynomials for these values. The improved nonlinear Aerodynamic Derivative model was validated by using the NACA 0015 airfoil and the F-18 model. The results show that the improved model has a higher prediction ability at high angles of attack and has the ability to predict the Aerodynamic characteristics of other unknown states based on known unsteady Aerodynamic data, such as the initial angle of attack, reduced frequency, and oscillation amplitude.